Abstract: A shaft assembly for a torque measurement system having a shaft that rotates is provided. The shaft assembly includes a cylinder fitted on to a shaft having flexible area, where the targets are formed after the cylinder is secured to the shaft and/or a cylinder mounting surface.

Abstract: A sensing system and method for detecting wear of an abradable layer on a stationary engine casing is provided. The system is capable of measuring the abradable thickness of the abradable layer by embedding abradable sensor in the abradable layer and measuring the changing electrical properties as the abradable sensor wears.

Abstract: Systems and methods for measuring torque on a drive train component of a rotating drive system are disclosed. In some aspects, a system includes a target assembly, a sensor assembly, and a sensor processing unit. The sensor assembly is located proximate to the target assembly, and the sensor assembly includes sensors mounted radially around the shaft and configured to detect sensor targets as the target assembly rotates with the drive train component. The sensor processing unit is configured for receiving sensor signals from the sensor assembly and outputting a torque signal based on the sensor signals. The sensor processing unit is configured for receiving target calibration data for the target assembly and sensor calibration data for the sensor assembly. The sensor processing unit is configured for verifying that the target calibration data corresponds to the target assembly and that the sensor calibration data corresponds to the sensor assembly.

Abstract: Systems and methods for measuring displacement parameters of rotating shafts and couplings are disclosed. In some aspects, a measurement system includes a shaft extended in a longitudinal direction and a target wheel configured to rotate with the shaft. The target wheel includes sensor targets circumferentially distributed around the target wheel. Some of the targets are slanted in the longitudinal direction and some of the targets are parallel to the longitudinal direction. The measurement system includes a sensor array including at least three sensors mounted radially around the shaft and configured to detect the sensor targets as the target wheel rotates with the shaft. The measurement system includes a controller configured to receive sensor signals from the sensors and determine, based on the sensor signals, at least an axial displacement measurement of the shaft in the longitudinal direction and a radial displacement measurement of the shaft.

Abstract: Systems and methods for measuring torque on a drive train component of a rotating drive system are disclosed. In some aspects, a system includes a target assembly, a sensor assembly, and a sensor processing unit. The sensor assembly is located proximate to the target assembly, and the sensor assembly includes sensors mounted radially around the shaft and configured to detect sensor targets as the target assembly rotates with the drive train component. The sensor processing unit is configured for receiving sensor signals from the sensor assembly and outputting a torque signal based on the sensor signals. The sensor processing unit is configured for receiving target calibration data for the target assembly and sensor calibration data for the sensor assembly. The sensor processing unit is configured for verifying that the target calibration data corresponds to the target assembly and that the sensor calibration data corresponds to the sensor assembly.

Abstract: Systems and methods for measuring displacement parameters of rotating shafts and couplings are disclosed. In some aspects, a measurement system includes a shaft extended in a longitudinal direction and a target wheel configured to rotate with the shaft. The target wheel includes sensor targets circumferentially distributed around the target wheel. Some of the targets are slanted in the longitudinal direction and some of the targets are parallel to the longitudinal direction. The measurement system includes a sensor array including at least three sensors mounted radially around the shaft and configured to detect the sensor targets as the target wheel rotates with the shaft. The measurement system includes a controller configured to receive sensor signals from the sensors and determine, based on the sensor signals, at least an axial displacement measurement of the shaft in the longitudinal direction and a radial displacement measurement of the shaft.

Abstract: Rotary motion sensing systems are well-suited for integration in a bearing system of a rotary aircraft to provide information about the operational state of the rotor blades of the aircraft. In some embodiments, sensors are positioned on lateral sides of an elastomeric bearing system and output signals which may be processed to calculate one or more rotor blade operational states. The operational states include, for example, flap angle, lead-lag angle, and pitch angle. In other embodiments, sensors may be distributed along at least a portion of the length of a rotor blade to detect deflection of the rotor blade or its impact with another object. The operational state of the rotor blades may be transmitted to the pilot and/or the flight control computer of the aircraft in order for corrective action to be taken and/or may be stored within a control box for later review.

Abstract: Helicopter rotating hub mounted vibration control system for a rotary wing hub having periodic vibrations while rotating at an operational rotation frequency. The vibration control system includes a housing attachable to the rotary wing hub and rotating with the hub at the operational frequency. The housing is centered about the rotary wing hub axis of rotation and has an electronics housing cavity subsystem and an adjacent rotor housing cavity subsystem. The rotor housing cavity contains a first coaxial ring motor with a first rotor and imbalance mass and a second coaxial ring motor with a second rotor and imbalance mass.

Abstract: Helicopter rotating hub mounted vibration control system for a rotary wing hub having periodic vibrations while rotating at an operational rotation frequency. The vibration control system includes a housing attachable to the rotary wing hub and rotating with the hub at the operational frequency. The housing is centered about the rotary wing hub axis of rotation and has an electronics housing cavity subsystem and an adjacent rotor housing cavity subsystem. The rotor housing cavity contains a first coaxial ring motor with a first rotor and imbalance mass and a second coaxial ring motor with a second rotor and imbalance mass.

Abstract: Helicopter rotating hub mounted vibration control system for a rotary wing hub having periodic vibrations while rotating at an operational rotation frequency. The vibration control system includes a housing attachable to the rotary wing hub and rotating with the hub at the operational frequency. The housing is centered about the rotary wing hub axis of rotation and has an electronics housing cavity subsystem and an adjacent rotor housing cavity subsystem. The rotor housing cavity contains a first coaxial ring motor with a first rotor and imbalance mass and a second coaxial ring motor with a second rotor and imbalance mass.

Abstract: Helicopter rotating hub mounted vibration control system for a rotary wing hub having periodic vibrations while rotating at an operational rotation frequency. The vibration control system includes a housing attachable to the rotary wing hub and rotating with the hub at the operational frequency. The housing is centered about the rotary wing hub axis of rotation and has an electronics housing cavity subsystem and an adjacent rotor housing cavity subsystem. The rotor housing cavity contains a first coaxial ring motor with a first rotor and imbalance mass and a second coaxial ring motor with a second rotor and imbalance mass.

Abstract: Helicopter rotating hub mounted vibration control system for a rotary wing hub having periodic vibrations while rotating at an operational rotation frequency. The vibration control system includes a housing attachable to the rotary wing hub and rotating with the hub at the operational frequency. The housing is centered about the rotary wing hub axis of rotation and has an electronics housing cavity subsystem and an adjacent rotor housing cavity subsystem. The rotor housing cavity contains a first coaxial ring motor with a first rotor and imbalance mass and a second coaxial ring motor with a second rotor and imbalance mass.

Abstract: Methods and systems for monitoring rotating shaft shafts and couplings in an aircraft propulsion system is described. The measurement system/method provides for accurate and precise monitoring of a rotating shaft flexible coupling in a fixed wing aircraft vehicle propulsion system. The measuring system/method provides for a high reliability short take off vertical landing fixed wing aircraft in which the vertical propulsion dynamically rotating drive shaft system and couplings are monitored in real time. The vehicular shaft coupling misalignment measuring system utilizes multiple positional sensors to provide highly reliable and precise determination of the dynamic characteristics of the rotating sensor target components of the propulsion system drive shaft. The relative position of the sensors is rigidly fixed externally from the rotating targets with a structural frame.

Abstract: A computer programmable system and program product for controlling vibrations is provided. The computer programmable system and program product include first program instructions for actively driving a first imbalance mass concentration rotor and a second imbalance mass concentration rotor at a vibration canceling rotation frequency while controlling the rotational position of the first imbalance mass concentration and the second imbalance mass concentration to produce a rotating net force vector to inhibit periodic vibrations. The computer programmable system and program product include second program instructions to opposingly orient the first imbalance mass concentration relative to the second imbalance mass concentration during a starting stopping rotation speed less than the vibration canceling rotation frequency. The system and product preferably include a fault mode control protocol for controlling a rotation of the rotors during a sensed failure of the rotating assembly vibration control system.

Abstract: A helicopter rotating hub mounted vibration control system for a helicopter rotary wing hub having a periodic vibration while rotating at a helicopter operational rotation frequency. The helicopter rotating hub mounted vibration control system includes an annular ring rotary housing attachable to the helicopter rotary wing hub and rotating with the helicopter rotary wing hub at the helicopter operational rotation frequency. The annular ring housing is centered about the rotary wing hub axis of rotation and has an electronics housing cavity subsystem and preferably an adjacent coaxial rotor housing cavity subsystem. The rotor housing cavity subsystem contains a first coaxial frameless AC ring motor having a first rotor with a first imbalance mass and a second coaxial frameless AC ring motor having a second rotor with a second imbalance mass.